高速大迎角动态气动特性是衡量新一代高机动飞行器性能的重要参数之一。
Dynamic aerodynamics characteristic is one of very important parameters of modern maneuverable aircraft to be scaled at high Angle of attack and high speed.
建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
标枪的气动阻力、升力随迎角增加而增加。
The aerodynamic drag and lift of javelin increase with angle of attack.
实际计算结果表明该非线性气动力模型能够较为精确地计算飞机模型大幅值迎角简谐振动产生的气动力响应。
It is shown the nonlinear aerodynamic model given by the article can accurately calculate aerodynamic responses of aircraft models in large amplitude forced oscillation tests at high angles of attack.
用一算例说明了估计过程，获得了纵向气动导数随迎角变化的估计结果。
The estimation procedure is shown by using an example and the estimation results of variation of longitudinal aerodynamic derivatives with Angle of attack are obtained.
有效迎角的减小又使得弹性机翼的有效气动力载荷减小。
The torsion reduces the effectual attack angle of the elastic sweep wing.
研究了在大迎角下，后掠翼对细长体绕流结构和气动力特性的影响。
The influence on flow structure and aerodynamic of a slender by sweep wing at high Angle of attack was studied.
当扑翼在小迎角飞行时，机翼带翼刀可以有效地改善扑翼的气动特性。
When flapping-wing flight at small attack Angle, wing had wing-blade improve effectively aerodynamic characteristic of flapping-wing.
通过风洞试验，对带升降副翼控制的自由翼气动特性也进行了实验研究，验证了位于自由翼后缘的升降副翼可有效地控制自由翼相对气流的平衡迎角。
The aerodynamic characteristics of the free wing are investigated in this paper. The wind tunnel test results shows that the control of the angle of attack of the fre…
试验中进行了扑动频率、风速、迎角、机翼平面形状、翼型弯度对机翼气动特性影响的研究。
The effects of flapping frequency, wind velocity, Angle of attack, plane shape of wing and cambered aerofoil are investigated.
而当迎角较小或超过抖振迎角后该激波控制鼓包不会对基本翼型的气动性能产生较大影响。
When the Angle of attack is small or more than Angle of attack of buffeting, the shock control bump has little effect on the dynamics of airfoil.
大迎角气动弹性分析是现代飞行器设计中非常引人瞩目并且复杂的研究课题。
Aeroelastic analysis at high angles of attack is an attractive and complicated research subject in modern aircraft design.
而当迎角较小或超过抖振迎角后该激波控制鼓包不会对基本翼型的气动性能产生较大影响。
When the Angle of attack is small or when it is larger than the buffet onset Angle, the shock control bump has little effect on the dynamics of the airfoil.
而当迎角较小或超过抖振迎角后该激波控制鼓包不会对基本翼型的气动性能产生较大影响。
When the Angle of attack is small or when it is larger than the buffet onset Angle, the shock control bump has little effect on the dynamics of the airfoil.
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